Cargo parachute release apparatus, system and method

ABSTRACT

A cargo parachute release apparatus comprising an assembly plate and a hinged member that is hinged to the assembly plate with a hinge pin. Parachute riser attachment components are positioned between the assembly plate and hinged member when the hinged member is in the closed position. An electronic package assembly having a microprocessor having predetermined parameters is provided, and the electronic package assembly has horizontal and vertical accelerometers and a strain gage for collecting data and sending the data to the microprocessor for processing. When the incoming data matches the predetermined parameters that indicate impact has been made, the microprocessor sends a firing signal to an electro-explosive device to detonate which causes the hinged member to open and release the parachute. The cargo is not dragged along the ground, tipped over or otherwise damaged.

CROSS REFERENCE TO RELATED APPLICATIONS

This application is a divisional of U.S. patent application Ser. No.11/471,757, filed Jun. 21, 2006 now U.S. Pat. No. 7,461,817, which isincorporated herein by reference, which claims priority to U.S.Provisional patent application No. 60/692,635, filed Jun. 21, 2005 toHansson et al., for a Cargo Parachute Release Apparatus, System andMethod which is incorporated herein by reference.

BACKGROUND

Some military cargo planes are designed so that cargo can be dropped outof them while the plane is airborne. The cargo is secured on pallets andextracted from the plane. As the cargo falls, parachutes deploy to slowthe descent. At some point after the cargo impacts land, the parachutesmust detach, otherwise the parachutes could drag the cargo or tip thecargo over.

Therefore, mechanical devices are used to release the parachutes fromthe cargo. A significant problem exists with the current systems becausethey have an unacceptable success rate, because parachuted drops ofcargo end up tipping over upon impact and roll on the ground, which candamage and/or ruin the cargo.

Thus, what is needed is a better apparatus for releasing parachutes fromcargo.

SUMMARY

The cargo parachute release apparatus, system, and method of thisinvention is capable of supporting about 25,000 pounds of cargo. Twoindividual cargo parachute release apparatuses can be connected or“piggybacked” to one another, so that cargo loads of up to about 50,000pounds can be supported. The cargo loads are placed on and secured topallets, and can include food, medicine, and heavy vehicles.

In a preferred embodiment, the cargo parachute release apparatus of theinvention comprises an assembly plate and a hinged member that areconnected to one another by a hinge pin, such that the hinged member ismovable between an open or release position and a closed position. Thehinged member has formations having bores. There is an electronicassembly or electronic package assembly (hereinafter EPA) from whichextend release pins, and the EPA is fitted in a recess formed in theassembly plate. The hinged member is moved into a closed position, suchthat the release pins extend from the EPA and are received in the boresin the formations. The hinged member is moved into the closed positionwhen the cargo parachute release is being assembled. In addition, whenthe hinged member is in the closed position, parachute riser attachmentcomponents that connect to the parachute are positioned in curvedrecesses that are formed in the assembly plate and the hinged member,respectively.

The assembly plate has a recess into which is fitted the EPA. One of thefunctions of the EPA is to determine when the parachute should releasefrom the cargo parachute apparatus. This is accomplished by a circuitassembly having a microprocessor, vertical and horizontalaccelerometers, a flash memory chip, a network of resistors forming astrain gage, a firing circuit, a voltage supervisor circuit and avoltage regulator network. There is also an electro-explosive device(hereinafter EED) positioned in the EPA. When the cargo is pushed fromthe aircraft the strain gage detects a voltage signal acts and this actsto “wake up” or activate the microprocessor to begin operation of theelectrical system. The processor thereafter begins to receive data fromthe vertical and horizontal accelerometers to sense the vertical andhorizontal movement of the descending parachute. The vertical andhorizontal accelerometers continuously send data to the microprocessorfor processing and evaluation. The microprocessor sends the incomingdata to a flash memory for storage after processing.

The microprocessor continues to monitor and process the incoming datafrom the vertical and horizontal accelerometers until the data indicatesthat the cargo has impacted with land or water. In particular, themicroprocessor has stored predetermined parameters and when the incomingdata matches the predetermined parameters, that is, the impact signal isdetected, the microprocessor sends a command signal to the firingcircuit, and the firing circuit activates or fires the EED.

The EPA includes a spring that forces on the release pins so that therelease pins extend from the EPA and into the bores in the formations inthe hinged member. When the EED fires, the gas causes the release pinsretract into the housing and the spring compresses, and the release pinsare thereafter held in the retracted position by pin retainers. When therelease pins retract they rapidly withdraw out of the bores in theformations in the hinged member. The hinged member is thus allowed toopen, and when this happens the parachute attachment riser componentsrelease and the parachute(s) detaches from the cargo.

When the parachute is dropped from a plane the parachute deploys, whichcauses a strain to be imparted through the parachute riser attachmentcausing the EPA to arm. Vertical and horizontal accelerometers measurethe rate and angle of descent and the strain gage measures the tensileload on the parachute attachment riser components. The microprocessorconstantly compares this incoming data with a set of storedpredetermined parameters. When the measured strain data and data inputsfrom the vertical and horizontal accelerometers match the predeterminedparameters stored in the microprocessor, the microprocessor sends afiring signal to the firing circuit which causes an explosive device todetonate. The release pins retract from the bores in the hinged member,and the hinged member opens and the parachute detaches.

In another embodiment, there can be a pin, pull pin or release pin thatconnects to a switch. When the cargo is extracted from the plane anddropped, the arming pin is pulled and this closes the switch causingcurrent to flow in the circuit assembly. Thus, the pulling the armingpin when the cargo is dropped activates the EPA. In addition, in such anembodiment the strain gage is not required, because the EPA is armedwhen the arming pin is pulled. Thus the EPA can be make without thestrain gage.

In yet another embodiment, the EPA can have both the strain gage asdescribed above, and the arming pin and switch which will provide for adegree of redundancy to arm the EPA.

Thus, the with the present invention the cargo is advantageously notdamaged, because the parachutes are detached at a the precise momentwhen the predetermined parameters are met, which prevents anysignificant damage to the cargo. The problems associated with winddragging and ruining cargo are thus advantageously eliminated by theinvention.

BRIEF DESCRIPTION OF THE FIGURES

At the outset, it is noted that like reference numbers are intended toidentify the same structure, portions, or surfaces consistentlythroughout the figures.

FIG. 1 is a perspective view of the cargo parachute release apparatuswherein the hinged member is in the closed position.

FIG. 2 is a rear elevational view, partly in broken line, of the cargoparachute release apparatus.

FIG. 3 is a perspective view of the cargo parachute release apparatuswherein the hinged member is in a partially open position.

FIG. 4 is a front elevational view, partly in broken line, of the cargoparachute release apparatus wherein the hinged member is in the fullyopen position.

FIG. 5 is a perspective view, partly in broken line, of the cargoparachute release apparatus wherein the hinged member is in the openposition.

FIG. 6 is a perspective view of the cargo parachute release apparatuswherein the hinged member is in the open position.

FIG. 7 is a front elevational view of the cargo parachute releaseapparatus wherein the hinged member is in the open position.

FIG. 8 is a right side elevational view of the cargo parachute releaseapparatus wherein the hinged member is in the open position.

FIG. 9 is a top plan view of the cargo parachute release apparatuswherein the hinged member is in the open position.

FIG. 10 is a diagrammatic view of the cargo parachute release joined toa parachute and cargo

FIG. 11 is a block diagram depicting the electronic system of the EPA.

FIGS. 12A-12G are portions of a circuit diagram of the EPA.

FIG. 13 is a portion of the circuit diagram for the verticalaccelerometer component of the EPA.

FIG. 14 is an exploded view of the components of the EPA.

FIG. 15 is a perspective view of the housing of the EPA.

FIG. 16 is a sectional view of the housing taken along cut line A-Ashown in FIG. 14.

FIG. 17 is an enlarged portion of FIG. 16 indicate by arrow B in FIG.16.

FIG. 18 is a perspective view of the latch pins and spring.

FIG. 19 is an exploded view of the release pin and release pin retainer.

FIG. 20 is a perspective view of the release pin and release pinretainer.

FIG. 21 is a perspective view of the release pin and release pinretainer showing gas flow openings in the release pin retainer.

FIG. 22 is a sectional view of the release pin positioned in the releasepin retainer taken along cut line C-C shown in FIG. 21.

DETAILED DESCRIPTION

As shown generally in FIGS. 1-9, in a preferred embodiment the cargoparachute release 20 of the invention has a mechanical assembly 21 thatincludes an assembly plate 22 and a hinged member 24 connected to oneanother by a hinge pin 26. The hinged member 24 is movable between anopen or release position 28 shown in FIGS. 3 and 4, and a closedposition 30 shown in FIG. 1. As shown in FIG. 5, the hinged member 24has release pin receiving formations 74 that have bores 75 that areadapted to receive release pins 34. The cargo parachute release 20 alsoincludes an EPA 32 from which the release pins 34 extend, and the EPA 32is fitted in a recess 70 formed in the assembly plate 22, as shown inFIGS. 4 and 5. The hinged member 24 is moved into a closed position 30,such that the release pins 34 extend from the EPA 32 and are received inthe bores 75 in the release pin receiving formations 74. It is pointedout that the hinged member 24 is moved into the closed position 30 at afactory when the cargo parachute release 20 is assembled. In addition,when the hinged member 24 is in the closed position 30, parachute riserattachment components 60 that connect to the parachute 102, shown inFIG. 10, are positioned in a first curved recess 56 formed in theassembly plate 22, as shown in FIG. 4, and a second curved recess 82formed in the hinged member 22, as shown in FIG. 6.

The assembly plate 22 has an EPA recess 70, as shown in FIGS. 4 and 5,that is sized to receive the EPA 32. The operation of the EPA 32 isdepicted in the block diagram of FIG. 11, and the circuitry of the EPA32 is shown in detail in FIGS. 12A-12G and 13. One of the functions ofthe EPA 32 is to determine when the parachute cargo release system 100should release the parachute 102, shown in FIG. 10, such that the cargo104 connected to the cargo parachute release 20 is not dragged or rolledalong the ground 106. As shown in the block diagram of FIG. 11, thetiming of the release of the parachute 102 is carried out by a circuitassembly 41 that includes a microprocessor 43, a vertical accelerometer45 and a horizontal accelerometer 47 (shown in FIGS. 12E and 13) thatcan detect the direction of motion of the cargo parachute release 20, aflash memory chip 49 (FIG. 12B), an RS232 interface 51 (shown in FIG.12A) that provides for transmitting and receiving, RS232 interfacesbeing well known to those having ordinary skill in the art, a network ofresistors forming a strain gage 53, a firing circuit 55, a voltagesupervisor section 57 and a voltage regulator network 59. A batteryconnector network assembly 61 (shown in FIG. 12F) receives power from abattery pack 63 and supplies power for the circuit assembly 41.

As shown in the flow chart of FIG. 11, the EPA 32 has the strain gage53, and the strain gage 53 is for detecting the sudden decelerationcaused when the parachute 102 opens as voltage and this voltage is sentto the microprocessor 43. The voltage acts to “wake up” or activate themicroprocessor 43 to begin operation of the circuit assembly 41. Inaddition, as will be described presently, an arming pin, pull pin orrelease pin as indicated in FIG. 11 at 53 a can be provided that, whenpulled during extraction of the cargo 104, can cause current to flow inthe circuit assembly 41. The microprocessor 43 activates the beginningmeasurements of the strain gage 53, the vertical accelerometer 45 andthe horizontal accelerometer 47 to sense the vertical and horizontalmovement of the descending cargo parachute 102 along with the strainimparted on the strain gage 53 from the parachute riser attachmentcomponents 60. The strain gage 53, vertical accelerometer 45 andhorizontal accelerometer 47 send data to the microprocessor 43 forprocessing and evaluation. The microprocessor 43 sends the data to theflash memory 49 for storage. Microprocessors, flash memories,accelerometers and strain gages are well known to those having ordinaryskill in the art.

The microprocessor 43 has predetermined stored impact signal parameters.The microprocessor 43 continuously monitors the incoming data from thevertical and horizontal accelerometers 45, 47, respectively, and straingage 53 until the vertical and horizontal accelerometers 45, 47,respectively, and strain gage 53 data match the predetermined impactsignal parameters. When the predetermined impact parameters are met, itis an indication that the cargo 104 has impacted with the ground 106(shown in FIG. 10) or water. Upon receiving the impact signal data, themicroprocessor 43 sends an electronic command signal to the firingcircuit 55, and this actuates an EED 65. The firing of the EED 65 causesthe release pins 34 to retract into the EPA 32 and move out of the bores75 in the hinged member 24, and this allows the hinged member 24 to moveto the open position 28. The EED 65 is an explosive charge that can bedetonated with an electronic signal, and when detonated the chargeretracts the release pins 34 into the EPA 32. The EED 65 can alsocomprise motive means for retracting the release pins 34 such that thehinged member 24 can open. For example, the EED 65 can be a solenoid, asindicated in FIG. 11 at 65 a, capable of retracting the release pins 34.Solenoids are well known to those having skill in the art.

FIGS. 12A-12G and 13 diagrammatically shows the circuit assembly 41. Asshown, the battery 63 supplies power to the battery connector network 61to power the circuit assembly 41. When the parachute 102 is dropped froman aircraft, the strain gage 53 sends a signal to the microprocessor 43,and the microprocessor 43 begins collecting incoming data from thevertical accelerometer 45, and horizontal accelerometer 47 and straingage 53. The microprocessor 43 processes the incoming data and stores itin the flash memory 49 for future reference. Voltage in the circuitassembly 41 is controlled by the voltage supervising circuit 57 and thevoltage regulator network 59. In particular, the voltage regulatornetwork 59 supplies a constant voltage to the circuit assembly 41, andthe voltage supervising circuit 57 serves to maintain correct voltagerequirements for the microprocessor 43. When the vertical accelerometer45, horizontal accelerometer 47 and strain gage 53 send a data thatmatches a predetermined impact signal to the microprocessor 43, themicroprocessor 43 sends a signal to the firing circuit 55. The firingcircuit 55, upon receiving the signal from the microprocessor 43, causesthe EED 65 to explode and cause the release pins 34 to withdraw from thebores 75 in the release pin receiving formations 74 in the hinged member24. As a result, the hinged member 24 moves to the open position 28 andthe parachute 102 releases from the cargo parachute release 20.

It is pointed out that the data received from the vertical accelerometer45, the horizontal accelerometer 47 and strain gage 53 provide a virtual“picture” of the direction of travel of the cargo parachute release 20as it falls, and this data is transmitted to the microprocessor 43 forprocessing and analysis. As previously mentioned, the microprocessor 43stores or contains predetermined firing and non-firing or holdingparameters, and the microprocessor 43 matches incoming data from thevertical accelerometer 45, horizontal accelerometer 47 and strain gage53 with these stored parameters. For example, if the strain gage 53shows a reduction in load, but the vertical accelerometer 45 andhorizontal accelerometer 47 accelerometer indicate a vertical velocityof 24 feet/second, the microprocessor 43 will not send a signal to thefiring circuit 55 to fire the EED 65. The above scenario could be causedif the parachute 102 collapses while falling, however, the verticalvelocity is an indicator that the assembly has not yet hit the ground.

In addition, as shown in FIG. 2, the EPA 32 contains a built-in test(hereinafter BIT) switch 69. A user pushes the BIT switch 69 and thebuilt in test checks the integrity of the circuit assembly 41, includingthe batteries and EED 65. If the BIT switch 69 flashes after beingpressed, this indicates that the cargo parachute release apparatus 20can be pushed from the plane and that the parachute will detach when thepredetermined parameters are met.

As shown in FIGS. 1 and 2, the cargo parachute release apparatus 20 hasa first side 36 and an opposed second side 38, and as shown in FIGS. 3-6the assembly plate 22 has a parachute attachment end wall 40 and anopposed cargo attachment end wall 42. Extending between the parachuteattachment end wall 40 and cargo attachment end wall 42 are opposedfirst and second edge walls 44, 46, respectively. Extending from each ofthe first and second edge walls 44, 46, respectively, are piggyback boltadapters, commonly designated 48. The piggyback bolt adapters 48 allowthe cargo parachute release apparatus 20 to be connected to other cargoparachute release apparatuses (not shown) with bolts, whichadvantageously increases the amount of cargo that can be dropped usingthe cargo parachute release 20. In the illustrative embodiment shownherein there are four such piggyback bolt adapters 48 extending from theopposed first and second edge walls 44, 46, respectively of the assemblyplate 22.

Extending from a position internal to the assembly plate 22 and throughthe cargo attachment end wall 42 are load brackets 50. One end of eachof the load brackets 50 is received in and bolted to the assembly plate22 with bolts 52, and the other end of each of the load brackets 50 isconnected to a cargo pallet attachment 54. The cargo pallet attachment54 points consist of a pin type arrangement that allow for various sizepallet straps (not shown) to be attached to the release apparatus 20.

As shown in FIGS. 3-6, the assembly plate 22 has formed therein a firstcurved race 56 adjacent the parachute attachment end wall 40. Theparachute attachment end wall 40 has a narrow portion 58. As will bedescribed presently, the first curved race 56 is for receiving parachuteriser attachment components 60. As shown in FIGS. 3 and 4, each of theparachute riser attachment components 60 has a ball-shaped portion 62joined to a riser attachment portion 64. The riser portion 64 has afastener 68 that connects to parachute risers (not shown) in a knownmanner.

Referring now to FIGS. 4 and 5, the assembly plate 22 has a recess 70sized to receive the EPA 32 therein. In particular, the recess 70 isdefined in the first side 36 of the assembly plate 22 between the firstcurved race 56 and the hinge pin 26, such that when the hinged member 24is the closed position 30 the EPA 32 is positioned in the recess 70 andbetween the assembly plate 22 and hinged member 24. As shown in FIG. 5,the EPA 32 is substantially flush with the surrounding assembly plate 22and is connected to the assembly plate 22 with, for example, bolts 72 asshown in FIG. 2. As shown in FIGS. 4 and 5, the release pins 34 extendfrom each side of the EPA 62. When the cargo parachute release apparatus20 is in the closed position 30, the release pins 34 are positioned inbores 75 of release pin receiving formations 74 that extend from thehinged member 24. The release pin receiving formations 74 are best shownin FIG. 5. When the release pins 34 are positioned in the release pinreceiving formations 74, the hinged member 24 is prevented from movingfrom the closed position 30 to the open position 28.

When the EPA 32 is subsequently fired, the release pins 34 are rapidlyretracted out of the release pin receiving portions 74 and into the EPA32, which thus allows the hinged member 24 to move from the closedposition 30 to the open position 30, which results in the release of theparachute riser attachment components 60. The release pins 34 seat inreplaceable roller bushings 94 shown in FIG. 14.

As shown in FIGS. 1 and 7, the hinged member 24 has a hinged end 76 andan opposed curved end 78 having a hinged member narrow portion 80. Asshown in FIGS. 5 and 6, the hinged member 24 has a second curved race 82that is adjacent to the narrow portion 80. As shown, the pair of releasepin receiving formations 74 extend from the hinged member 24 between thesecond curved race 82 and the hinged end 76.

In use, prior to closing the hinged member 24 and assembly plate 22together, the parachute riser attachment components 60 are positioned inthe assembly plate 22, such that the ball portions 62 are positioned inthe assembly plate first curved race 56. FIG. 3 shows three suchparachute riser attachment components 60, and in another illustrativeembodiment (not shown) there may be five parachute riser attachmentcomponents 60.

Upon closing the hinged member 24, the ball portions 62 move into thesecond curved race 82, such that the ball portions 62 are positioned inthe recess defined by the first and second curved races 56, 82,respectively. In addition, as shown in FIG. 1, a slot 84 is definedbetween the hinged member narrow portion 80 and the assembly platenarrow 58. The slot 84 is sized such that the parachute riser attachmentcomponents 60 can extend through the slot 84 and move back and forthalong the slot 84, but the ball portions 62 joined to the riserattachment portions 64 cannot pass through the slot 84.

When the cargo parachute release apparatus is in the closed position 30shown in FIG. 1, the release pins 34 are positioned in the release pinreceiving formations 74 extending from the hinged member 24. The hingepin 26 bears a portion of the load under which the cargo parachuterelease apparatus 20 is placed, allowing for decreased frictional forcesbetween the release pins 34 and the release pin receiving formations 74.It is pointed out that the release pins 34 are positioned in the pinreceiving formations 74.

After the release apparatus 20 has been actuated, the EPA 32 can bereadily removed and replaced or refurbished by replacing the EED 65,allowing for field or depot level refurbishment. These roller bushings94, shown in FIG. 19, can be scored or otherwise damaged by the releasepins 34 during actuation and the roller bushings 94 are thereforereplaceable. In addition, the roller bushings 94 provide for decreasedfriction between the release pins 34 and assembly plate 22 so that thereis a lower release force on these release pins 34 during actuation.

FIG. 14 is an exploded view the EPA 32. The EPA 32 has a housing 33 thatis sized to be received in the recess 70 of the assembly plate 22. Thebattery pack 63 is positioned in the housing 33 and the circuit assembly41 is mounted in the housing 33. As shown in FIGS. 15-17, the housing 33is provided with a housing recess 110. A seal 112 is positioned betweenthe housing 33 and a seal plate 114. The housing 33 also has opposedrelease pin walls 116 each having a bore 118.

As shown in FIG. 15, the housing 33 has a housing recess 120, and theseal plate can be connected to the housing 33. The housing recess 120extends to an EED recess 122 that is sized to receive the EED 65. Asshown in FIGS. 16 and 17, the EED recess 122 extends to a elongatepassage 124. The elongate passage 124 extends to release pin passages126 that are angled in a direction away from the elongate passage 124.As shown in FIG. 17, in one of the preferred embodiments the release pinpassage 126 make about a 45° angle with the elongate passage 124. Therelease pin passages 126 extend to the bores 118. In addition, theelongate passage 124 meets with plug recess passages 128 that are forreceiving gas port cover plugs 130, and shown in FIG. 19. As will bedescribed presently, the elongate passage 124 and release pin passage126 are for allowing the flow of pressured gas when the EED 65 isdetonated.

As shown in FIGS. 18-22, the bores 118 are sized to receive release pinretainers 132 having retainer openings 134, and the retainer openings134 are sized to receive the release pins 34. The release pin retainers132 are treaded to the housing 33, and in particular, into the bores118. Moving from left to right in FIG. 19, between the release pin 34and the release pin retainer 134 is an O-ring 140, and inner O-ring 142and an outer O-ring 144. The outer O-ring 144 is positioned around therelease pin retainer 134, the O-ring 140 is positioned around a largerdiameter portion 146 of the release pin 34 and the inner O-ring 142 ispositioned around a smaller diameter portion 148 of the release pin 34.A spring 146 is provided that, as shown in FIG. 18, forces on the largerdiameter portions 146 of the release pins 34.

Shown in FIGS. 20-22, the arrangement of the release pin 34 and therelease pin retainer 134. There is a pressurization space 150 definedbetween the release pin 34 and the release pin retainer 134. The releasepin retainer 134 has gas flow ports 152 as shown in FIG. 21. The gasflow ports 152 are for accommodating the flow of gas when the EED 65explodes. In particular, when the EED 65 explodes, the pressurized gasflows through the elongate passage 124 and then through the release pinpassages 126. From there, the pressurized gas flows through the gas flowports 152 in the release pin retainer 134 and into the pressure chamber150. Once in the pressure chamber 150 the pressurized gas forces on therelease pin 34, and the release pins 34 are caused to move in adirection toward one another and compress the spring 146, and they moveor retract into the housing 33. There is a key mechanism 152 thatreleases piston retainers 154 that retain the release pins 34 in thehousing 33, that is, in the retracted position. Thus, after detonationof the EED 65, the release pins 34 retract, the hinged member 24 opens,and the parachute 102 is released. In one of the preferred embodimentsthe entire release process takes about one second. There is also ahousing backing 156 provided with a label 158.

The EED 65 is a replaceable component. Once the cargo parachute releaseapparatus 20 has been used and the EED 65 fired, the EED 65 can beadvantageously replaced and the EPA 32 can be reused, which saves on thecosts associated with using the cargo parachute release apparatus 20.

In another embodiment, there can be an arming pin, pull pin or releasepin as indicated in FIG. 11 at 53 a that connects to a switch (notshown). When the cargo 104 is extracted from the plane and dropped, thearming pin is pulled and this closes the switch causing current to flowin the circuit assembly 41. Thus, the pulling the arming pin when thecargo 104 is dropped activates the EPA 32. In addition, in such anembodiment the strain gage 53 is not required, because the EPA 32 isarmed when the arming pin is pulled. Thus the EPA 32 can be made withoutthe strain gage.

In yet another embodiment, the EPA 32 can have both the strain gage 53as described above, and the above-described arming pin indicated in FIG.11 at 53 a and switch which will provide for a degree of redundancy toarm the EPA 32.

Thus, the present cargo parachute release 20 advantageously releases aparachute 102 at the precise moment such that the cargo 104 is notdragged or rolled upon impacting the ground 106, which advantageouslyprotects the cargo 104 from damage.

It will be appreciated by those skilled in the art that while a cargoparachute release apparatus has been described above in connection withparticular embodiments and examples, it is not necessarily so limited,and other embodiments, examples, uses, and modifications and departuresfrom the embodiments, examples, and uses may be made within the scopeand spirit of the present invention.

1. A method of making a cargo parachute release apparatus comprising:providing an assembly plate having a recess; providing a hinged memberand connecting the hinged member to the assembly plate with a hinge pinsuch that the hinged member is movable between open and closed positionsand forming release pin receiving formations having bores on the hingedmember; providing an electronic package assembly having release pins andpositioning the electronic package assembly in the recess such that in aclosed position of the hinged member the release pins are located in thebores of the release pin receiving formations such that the hingedmember is held in the closed position; and providing the electronicpackage assembly with a microprocessor with at least one predeterminedparameter, the electronic package assembly including a strain gauge, andvertical and horizontal accelerometers for providing signals to themicroprocessor, the electronic package assembly further including anelectro-explosive device such that when the microprocessor detectssignals from the strain gauge and vertical and horizontal accelerometersthat match the predetermined parameter the electro-explosive devicedetonates retracting the release pins from the bores which allows thehinged member to move to the open position and release the parachutefrom the cargo.
 2. A method of making a cargo parachute releaseapparatus comprising: providing an assembly plate having a recess;providing a hinged member and connecting the hinged member to theassembly plate with a hinge pin such that the hinged member is movablebetween open and closed positions and forming release pin receivingformations having bores on the hinged member; providing an electronicpackage assembly having release pins and positioning the electronicpackage assembly in the recess such that in a closed position of thehinged member the release pins are located in the bores of the releasepin receiving formations such that the hinged member is held in theclosed position; and providing the electronic package assembly with amicroprocessor with at least one predetermined parameter, at least onesensor and an electro-explosive device such that when the microprocessordetects a signal from the sensor that matches the predeterminedparameter the electro-explosive device detonates retracting the releasepins from the bores which allows the hinged member to move to the openposition and release the parachute from the cargo; and providing theassembly plate with at least one first race and providing the hingedmember with at least one second race and forming a slot between thehinged member and the assembly plate when the hinged member is in theclosed position.
 3. The method according to claim 2, further includingextending the slot to the at least one first race and the at least onesecond race.
 4. Then method according to claim 3, further includingproviding a parachute riser attachment component having a ball portionand a riser portion and positioning the parachute riser component suchthat when the hinged member is in the closed position the ball portionis positioned in the at least one first race and the at least one secondrace and the riser portion is positioned in the slot.
 5. The methodaccording to claim 4, wherein the parachute riser component is capableof being attached to a parachute.
 6. The method according to claim 1,wherein the electro-explosive device is replaced with pressurized gas ora solenoid capable of being detonated upon receiving a firing signalfrom the microprocessor.
 7. The method according to claim 1, wherein theelectronic package assembly includes a sensor for detecting strain andacceleration in three different axes.
 8. The method according to claim1, further including providing the electronic package assembly to bereusable.